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TECHNICAL PAPERS

Aerodynamic Loss Characteristics of a Turbine Blade With Trailing Edge Coolant Ejection: Part 1—Effect of Cut-Back Length, Spanwise Rib Spacing, Free-Stream Reynolds Number, and Chordwise Rib Length on Discharge Coefficients

[+] Author and Article Information
Oguz Uzol, Cengiz Camci

Turbomachinery Heat Transfer Laboratory, The Pennsylvania State University, University Park, PA 16802

Boris Glezer

Heat Transfer Team Leader, Solar Turbines, Inc., San Diego, CA 92186

J. Turbomach 123(2), 238-248 (Feb 01, 2000) (11 pages) doi:10.1115/1.1348017 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Metzger, D. E., Kim, Y. W., and Yu, Y., 1993, “Turbine Cooling: An Overview and Some Focus Topics,” Proc. 1993 International Symposium on Transport Phenomena in Thermal Engineering.
McMartin, I. P., and Norbury, J. F., 1974, “The Aerodynamics of a Turbine Cascade With Supersonic Discharge and Trailing Edge Blowing,” ASME Paper No. 74-GT-120.
Prust, H. W., 1975, “Cold Air Study of the Effect on Turbine Stator Blade Aerodynamic Performance of Coolant Ejection from Various Trailing Edge Slot Geometries, Part II: Comparison of Experimental and Analytical Results,” NASA Paper No. TM-X-3190.
Lokai,  V. I., and Kumirov,  B. A., 1973, “Losses in Turbine Cascades With Cooling Air Discharge and Various Trailing Edge Geometries,” Soviet Aeronautics (English translation of Izvestiya VUZ Aviatsionnaya Tekhnika), 16, No. 3, pp. 64–67.
Lawaczek, O., 1977, “The influence of Jets of Cooling Air Exhausted From the Trailing Edges of a Supercritical Turbine Cascade on the Aerodynamical Data,” AGARD CP229, Paper No. 30.
Sturedus, C. J., 1979, “Aerodynamic Effects of Surface Cooling-Flow Injection on Turbine Transonic Flow Fields,” AIAA paper No. 79-1210.
Moses, H. L., Kiss, T., Bertsch, R., and Gergory, B. A. 1991, “Aerodynamic Losses Due to Pressure Side Coolant Ejection in a Transonic Turbine Cascade,” AIAA Paper No. 91-2032.
Venediktov,  V. D., 1972, “Investigating a Turbine Stage With Cooling Air Leaving Through Slots in the Concave Surfaces of the Nozzle Blades,” Thermal Engineering (English translation of Teploenergetika), 19, No. 7, pp. 20–25.
Kiock, R., Hoheisel, H., Dietrichs, H. J., and Holmes, A. T., 1985, “The Boundary Layer Behavior of an Advanced Gas Turbine Rotor Blade Under the Influence of Simulated Film Cooling,” AGARD Conf. Proc. No. 390, Heat Transfer and Cooling in Gas Turbines, pp. 42-1–42-19.
Wifert,  G., and Fottner,  L., 1996, “The Aerodynamic Mixing Effect of Dis-crete Cooling Jets With Mainstream Flow on a Highly Loaded Turbine Blade,” ASME J. Turbomach., 118, pp. 468–477.
Gaugler, R. E., and Russell, L. M., 1980, “Streakline Flow Visualization Study of a Horseshoe Vortex in a Large-Scale, Two-Dimensional Turbine Stator Cascade,” ASME Paper No. 80-GT-4.
Hippensteele, S. A., Russell, L. M., and Torres, F . J., 1985, “Local Heat Transfer Measurements on a Large, Scale-Model Turbine Blade Airfoil Using a Composite of a Heater Element and Liquid Crystals,” NASA T M 86900.
Uzol,  O., and Camci,  C., 2000, “Aerodynamic Loss Characteristics of a Turbine Blade With Trailing Edge Coolant Ejection: Part 2—External Aerodynamics, Total Pressure Losses, and Predictions,” ASME J. Turbomach., 123, this issue, pp. 249–257.

Figures

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Trailing edge details and throat section
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Trailing edge cooling system and plenum chamber details
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Cut-back configurations and the trailing edge cavity
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Four different cut-back lengths
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Three different rib arrangements (Models A, B, C)
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Discharge coefficients for Model A
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Discharge coefficients for model B
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Discharge coefficients for model C
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Actual coolant mass flow rate ratio versus pressure ratio (model A, Covers 1 and 4)
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Five different rib lengths (Model C, Cover 2)
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Influence of rib length on discharge coefficients (Model C, Cover 2)
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Discharge coefficients versus coolant to free-stream mass flow rate ratio (model C, Cover 2, data for all five rib lengths)
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Actual coolant mass flow rate versus pressure ratio (Model C, Cover 2, data for all five rib lengths)
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Spanwise total pressure uniformity at the trailing edge

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